Coupled linear parameter varying and flatness-based approach for space re-entry vehicles guidance
Coupled linear parameter varying and flatness-based approach for space re-entry vehicles guidance
- Author(s): M. Zerar ; F. Cazaurang ; A. Zolghadri
- DOI: 10.1049/iet-cta.2008.0057
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- Author(s): M. Zerar 1 ; F. Cazaurang 2 ; A. Zolghadri 2
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View affiliations
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Affiliations:
1: CreSTIC-URCA lab./Reims University, Reims, France
2: IMS lab./Bordeaux University, Talence, France
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Affiliations:
1: CreSTIC-URCA lab./Reims University, Reims, France
- Source:
Volume 3, Issue 8,
August 2009,
p.
1081 – 1092
DOI: 10.1049/iet-cta.2008.0057 , Print ISSN 1751-8644, Online ISSN 1751-8652
An linear parameter varying guidance method for the hypersonic phase of a space re-entry vehicle is presented. The suggested guidance scheme, relying on flatness approach, is applied to the non-linear model of the European Atmospheric Re-entry Demonstrator. It is shown that the overall guidance scheme achieves robust stability and performance, even in the presence of entry point kinematics dispersions. The design problem is formulated and solved using a finite set of linear matrix inequalities. Finally, Monte Carlo simulation results are presented to demonstrate the effectiveness of the suggested approach.
Inspec keywords: path planning; nonlinear control systems; Monte Carlo methods; linear matrix inequalities; space vehicles; robust control; vehicle dynamics
Other keywords:
Subjects: Algebra; Nonlinear control systems; Aerospace industry; Algebra; Stability in control theory; Statistics; Vehicle mechanics; Aerospace control; Control technology and theory (production); Spatial variables control; Monte Carlo methods
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